CN104764043A - Cooling air flame stabilization device for combustion chamber of gas turbine - Google Patents
Cooling air flame stabilization device for combustion chamber of gas turbine Download PDFInfo
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- CN104764043A CN104764043A CN201510150221.1A CN201510150221A CN104764043A CN 104764043 A CN104764043 A CN 104764043A CN 201510150221 A CN201510150221 A CN 201510150221A CN 104764043 A CN104764043 A CN 104764043A
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- central nozzle
- combustion chamber
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Abstract
The invention relates to the technical field of gas turbines, in particular to a cooling air flame stabilization device for a combustion chamber of a gas turbine. The cooling air flame stabilization device for the combustion chamber of the gas turbine comprises a central nozzle and an annular peripheral nozzle which is concentrically arranged on the outer side of the central nozzle, wherein a cooling air introduction unit is arranged at the front end of the central nozzle to introduce a small amount of cooling air from an air compressor, a combustion compression cylinder or an external air source; the cooling air enters a hollow pipeline in the outer wall of the central nozzle and is sprayed out from an oblique hole or an oblique slot in the tail end to form a conical cooling air flow of a fixed angle on the downstream side of the central nozzle; the flows of the central nozzle and the peripheral nozzle can be effectively isolated, and an expansion region is formed on the downstream side of the central nozzle, so the flow of the central nozzle is slowed and pressurized to form a stable reflow region and enhance the flame stabilization performance of the central nozzle; the introduced cold air flow flows towards the downstream side and finally still participates in combustion, so the waste of pure cooling air is reduced and the total performance of the combustion chamber is improved.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to the steady flame device of a kind of gas-turbine combustion chamber cold gas.
Background technology
Because the requirement of environmental protection is more and more stricter, in gas-turbine combustion chamber in recent years, use the mode of premixed combustion to reduce the discharge of nitrogen oxide (NOx) more and more.Adopt in the head of combustion chamber structure of premixed combustion mode typical, generally comprise one and be arranged in the central nozzle at center and multiple peripheral injector nozzles being arranged in central nozzle surrounding equably.Peripheral injector nozzles generally adopts premixed combustion mode to discharge with decreasing pollution thing, central nozzle adopts diffusion combustion mode or premixed combustion mode, nozzle downstream forms stable flame, and the kindling material generating premixed flame as peripheral injector nozzles uses, and maintains premixed combustion thus.
Existing gas-turbine combustion chamber arranges the steady flame plate of taper in central nozzle downstream, stabilize the flame to create formation recirculating zone, a deceleration diffusion district.But there is burning in the steady flame intralamellar part of taper, the wall surface temperature of the steady flame plate of taper can significantly rise, and therefore needs to cool this wall.Patent US8113000 introduces cold gas and cools this wall outside the steady flame plate of taper, and when chamber performance promotes, the cooling tolerance of the steady flame plate of taper can increase, and decreases burning gas, can cause the change of head assignment of traffic simultaneously.
Therefore, for above deficiency, the invention provides the steady flame device of a kind of gas-turbine combustion chamber cold gas.
Summary of the invention
(1) technical problem that will solve
The object of this invention is to provide a kind of steady flame device of gas-turbine combustion chamber cold gas saved the steady flame device setting of tradition, reduce the state combustion stability of cold gas consumption and raising combustion chamber.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides the steady flame device of a kind of gas-turbine combustion chamber cold gas, the annular peripheral nozzle that it comprises central nozzle, central nozzle outer concentric is arranged, and first cold gas introduce unit, the outer wall of described central nozzle is hollow pipe, described central nozzle the port of export be inclined hole or R-joining, described central nozzle entrance point introduce unit with the first cold gas and be communicated with.
Wherein, described inclined hole or R-joining outward-dipping, to spray outwardly taper cooling blast.
Wherein, described annular peripheral nozzle comprises internal layer annular peripheral injector nozzles and outer annular peripheral injector nozzles, and the outer wall of internal layer annular peripheral injector nozzles is hollow pipe, and the port of export of the hollow pipe of internal layer annular peripheral injector nozzles is inclined hole or R-joining; The eddy flow angle of outer annular peripheral injector nozzles is greater than the eddy flow angle of internal layer annular peripheral injector nozzles.
Wherein, also comprise the second cold gas and introduce unit, described internal layer annular peripheral injector nozzles entrance point connects the second cold gas and introduces unit.
Wherein, the leading portion that described first cold gas introduces unit is communicated with cooling source of the gas, and stage casing is a shrink nozzle or Laval nozzle, and back segment is communicated with the hollow pipe of central nozzle outer wall; The leading portion that described second cold gas introduces unit is communicated with cooling source of the gas, and stage casing is a shrink nozzle or Laval nozzle, and back segment is communicated with the hollow pipe of internal layer annular peripheral injector nozzles.
Wherein, described first cold gas is introduced between the leading portion of unit and the second cold gas introducing unit and stage casing and is also provided with pressure-producing part; Cold gas pressure ratio in described leading portion and stage casing is sub-critical values.
Wherein, described Laval nozzle produces supersonic flow.
Wherein, the eddy flow angle of described annular peripheral nozzle is greater than the eddy flow angle of central nozzle.
Wherein, the angle of described inclined hole or R-joining and central nozzle axis is between 20 ° ~ 45 °, and the perforated area of nozzle end end face or R-joining area account for 20% ~ 50% of the nozzle end end face gross area, and inclined hole aperture or R-joining width are between 2 ~ 5mm.
(3) beneficial effect
Technique scheme tool of the present invention has the following advantages: in the steady flame device of gas-turbine combustion chamber cold gas provided by the invention, first cold gas is set in central nozzle front end and introduces unit, from compressor, combustion cylinder pressure or external air source introduce a small amount of cold gas, introduce unit through the first cold gas to accelerate, enter the hollow pipe in central nozzle outer wall, finally from inclined hole or the R-joining ejection of center outer nozzle wall end, the taper cooling blast of a fixed angle is formed in central nozzle downstream, this air-flow replaces the steady flame plate of traditional solid vertebral plate, effectively can separate the flowing of central nozzle and peripheral injector nozzles, an expansion regions is formed in central nozzle downstream, make the flowing deceleration supercharging of central nozzle, form a stable recirculating zone, strengthen the steady flame performance of central nozzle, the cooling blast flow further downstream introduced, finally still participates in burning, decreases the waste of simple cold gas, improve combustion chamber overall performance, adopt this structure to also save the Cooling Design of the steady flame device of tradition, improve the life-span of head of combustion chamber structure, enhance the adaptability of interior outer nozzle, this combustion mode adopts the structure of circumferential equally distributed multi-layer rotational flow burning, reduces combustion chamber circumference burning concussion, improves the Dynamic Burning stability of combustion chamber.
Accompanying drawing explanation
Fig. 1 is the head of combustion chamber structural representation comprising the steady flame device of gas-turbine combustion chamber cold gas of the present invention;
Fig. 2 is the sectional view of the steady flame device of gas-turbine combustion chamber cold gas of the present invention.
In figure, 1: central nozzle; 2: internal layer annular peripheral injector nozzles; 3: outer annular peripheral injector nozzles; 4: the first cold gas introduce unit; 5; Pressure-producing part; 6: shrink nozzle; 7: R-joining; 101: central nozzle outer wall; 201: internal layer annular peripheral injector nozzles outer wall.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following examples for illustration of the present invention, but are not used for limiting the scope of the invention.
As depicted in figs. 1 and 2, the annular peripheral nozzle that the steady flame device central nozzle 1 of gas-turbine combustion chamber cold gas provided by the invention, central nozzle 1 outer concentric are arranged, and first cold gas introduce unit 4, the outer wall of described central nozzle 1 is hollow pipe, the port of export of hollow pipe is inclined hole or R-joining 7, and entrance point and first cold gas of hollow pipe are introduced unit 4 and be communicated with.Wherein, described inclined hole or R-joining 7 outward-dipping, to spray outwardly taper cooling blast.
In above-described embodiment, first cold gas is set at the entrance point of the hollow pipe of central nozzle 1 and introduces unit 4, from compressor, combustion cylinder pressure or other external air source introduce a small amount of cold gas, enter the hollow pipe in central nozzle outer wall 101, the final inclined hole from the port of export of center outer nozzle wall 101 hollow pipe or R-joining 7 spray, the taper cooling blast of a fixed angle is formed in central nozzle 1 downstream, this air-flow replaces the steady flame plate of traditional solid vertebral plate, effectively can separate the flowing of central nozzle 1 and peripheral injector nozzles, an expansion regions is formed in central nozzle 1 downstream, make the flowing deceleration supercharging of central nozzle 1, form a stable recirculating zone, strengthen the steady flame performance of central nozzle 1, and the cooling blast flow further downstream introduced, final participation burning, decrease the waste of simple cold gas, improve combustion chamber overall performance, in addition this structure is adopted to also save the Cooling Design of the steady flame device of tradition, improve the life-span of head of combustion chamber structure, enhance the adaptability of interior outer nozzle, in addition, annular peripheral nozzle is arranged with central nozzle 1 is concentric, compact conformation, and can be the flame envelope environment that central nozzle 1 provides stable.
Further, in the steady flame device of gas-turbine combustion chamber cold gas that the present embodiment provides, annular peripheral nozzle comprises internal layer annular peripheral injector nozzles 2 and outer annular peripheral injector nozzles 3, both are arranged all with one heart in the outside of central nozzle 1, internal layer annular peripheral injector nozzles outer wall 201 is hollow pipe, internal layer annular peripheral injector nozzles outer wall 201 end arranges R-joining 7, internal layer annular peripheral injector nozzles 2 front end arranges the second cold gas and introduces unit, it is identical that this second cold gas introducing unit and the first cold gas introduce unit 4 structure, the eddy flow angle of internal layer annular peripheral injector nozzles 2 is greater than the eddy flow angle of central nozzle 1, the eddy flow angle of outer annular peripheral injector nozzles 3 is greater than the eddy flow angle of internal layer annular peripheral injector nozzles 2, to avoid central nozzle 1, internal layer annular peripheral injector nozzles 2 and outer annular peripheral injector nozzles 3 spray the mutual interference of cold gas or flame, this combustion mode adopts the structure of circumferential equally distributed multi-layer rotational flow burning, reduces combustion chamber circumference burning concussion, improves the Dynamic Burning stability of combustion chamber.
Particularly, the leading portion that described first cold gas introduces unit 4 is communicated with cooling source of the gas, and stage casing is a shrink nozzle 6 or Laval nozzle, and back segment is communicated with the hollow pipe of central nozzle outer wall 101; The leading portion that described second cold gas introduces unit is communicated with cooling source of the gas, and stage casing is a shrink nozzle 6 or Laval nozzle, and back segment is communicated with the hollow pipe of internal layer annular peripheral injector nozzles 2; Described first cold gas is introduced between the leading portion of unit 4 and the second cold gas introducing unit and stage casing and is also provided with pressure-producing part 5; Cold gas pressure ratio in described leading portion and stage casing is sub-critical values, thus can eject Fast Cooling gas, and be subsonic speed from the air-flow velocity of central nozzle 1 end ejection, although velocity ratio is higher, combustion characteristics does not change, and can not have the impact of essence on combustion field.Second cold gas is introduced unit and the first cold gas and is introduced the cooling gas flow that unit 4 introduces and account for 2% ~ 8% of combustion chamber total flow, cools tolerance lower, affects less, can directly apply and the gas-turbine combustion chamber designed burning tissues and distribution.
Preferably, the R-joining 7 of central nozzle outer wall 101 and internal layer annular peripheral injector nozzles outer wall 201 end and the angle of this device axis are between 20 ° ~ 45 °, the width of R-joining 7 is between 2 ~ 5mm, and perforated area or R-joining 7 area of nozzle end end face account for 20% ~ 50% of the nozzle end end face gross area.The cone angle formed from the air-flow of central nozzle 1 and the ejection of internal layer annular peripheral injector nozzles 2 end, between 20 ° ~ 45 °, can play steady flame effect preferably.Meanwhile, by limiting width and the area of R-joining 7, the steady flame effect of needs can be reached with minimum air conditioning quantity.
The course of work of the steady flame device of gas-turbine combustion chamber cold gas of the present invention is as follows: the first cold gas introduces unit 4 and the second cold gas introducing unit can be bled from combustion cylinder pressure or be supplied by external air source; Cold gas is after pressure-producing part 5 pressurizes, enter shrink nozzle 6 or Laval nozzle, air-flow accelerates under elevated pressure conditions, hollow pipe finally through central nozzle outer wall 101 and internal layer annular peripheral injector nozzles outer wall 201 sprays at a high speed central nozzle outer wall 101 end, form the steady flame air-flow of taper, mainstream gas stream enters from central nozzle 1 and two-layer peripheral injector nozzles respectively, finally by taper steady flame air-flow be separated into interior, in, outer three laminar flows move; It has the following advantages and the technique effect of high-lighting: taper steady flame air current flow speed is very high, larger distance is gone out in chemical time, the flowing of effective separation central nozzle 1 and peripheral injector nozzles, a recirculating zone is formed in central nozzle 1 downstream, strengthen the steady flame performance of central nozzle 1, and this air-flow finally can participate in the combustion reaction in certain distance downstream, simplify the Cooling Design of steady flame structure on the one hand, do not cause the waste of cold gas on the other hand, therefore improve the combustibility of whole combustion chamber; This combustion mode adopts the structure of circumferential equally distributed multi-layer rotational flow burning, reduces combustion chamber circumference burning concussion, improves the Dynamic Burning stability of combustion chamber.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and modification, these improve and modification also should be considered as protection scope of the present invention.
Claims (9)
1. the steady flame device of gas-turbine combustion chamber cold gas, it is characterized in that: the annular peripheral nozzle that it comprises central nozzle, central nozzle outer concentric is arranged, and first cold gas introduce unit, the outer wall of described central nozzle is hollow pipe, described central nozzle the port of export be inclined hole or R-joining, described central nozzle entrance point introduce unit with the first cold gas and be communicated with.
2. the steady flame device of gas-turbine combustion chamber cold gas according to claim 1, is characterized in that: described inclined hole or R-joining outward-dipping, to spray outwardly taper cooling blast.
3. the steady flame device of gas-turbine combustion chamber cold gas according to claim 2, it is characterized in that: described annular peripheral nozzle comprises internal layer annular peripheral injector nozzles and outer annular peripheral injector nozzles, the outer wall of internal layer annular peripheral injector nozzles is hollow pipe, and the port of export of the hollow pipe of internal layer annular peripheral injector nozzles is inclined hole or R-joining; The eddy flow angle of outer annular peripheral injector nozzles is greater than the eddy flow angle of internal layer annular peripheral injector nozzles.
4. the steady flame device of gas-turbine combustion chamber cold gas according to claim 3, is characterized in that: also comprise the second cold gas and introduce unit, and described internal layer annular peripheral injector nozzles entrance point connects the second cold gas and introduces unit.
5. the steady flame device of gas-turbine combustion chamber cold gas according to claim 4, it is characterized in that: the leading portion that described first cold gas introduces unit is communicated with cooling source of the gas, stage casing is a shrink nozzle or Laval nozzle, and back segment is communicated with the hollow pipe of central nozzle outer wall; The leading portion that described second cold gas introduces unit is communicated with cooling source of the gas, and stage casing is a shrink nozzle or Laval nozzle, and back segment is communicated with the hollow pipe of internal layer annular peripheral injector nozzles.
6. the steady flame device of gas-turbine combustion chamber cold gas according to claim 5, is characterized in that: described first cold gas is introduced between the leading portion of unit and the second cold gas introducing unit and stage casing and is also provided with pressure-producing part; Cold gas pressure ratio in described leading portion and stage casing is sub-critical values.
7. the steady flame device of gas-turbine combustion chamber cold gas according to claim 6, is characterized in that: described Laval nozzle produces supersonic flow.
8. the steady flame device of gas-turbine combustion chamber cold gas according to claim 1, is characterized in that: the eddy flow angle of described annular peripheral nozzle is greater than the eddy flow angle of central nozzle.
9. the steady flame device of gas-turbine combustion chamber cold gas according to any one of claim 1-8, it is characterized in that: the angle of described inclined hole or R-joining and central nozzle axis is between 20 ° ~ 45 °, the perforated area of nozzle end end face or R-joining area account for 20% ~ 50% of the nozzle end end face gross area, and inclined hole aperture or R-joining width are between 2 ~ 5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510150221.1A CN104764043B (en) | 2015-03-31 | 2015-03-31 | Cooling gas flame stabilizing device for combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510150221.1A CN104764043B (en) | 2015-03-31 | 2015-03-31 | Cooling gas flame stabilizing device for combustion chamber of gas turbine |
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| CN104764043A true CN104764043A (en) | 2015-07-08 |
| CN104764043B CN104764043B (en) | 2022-10-21 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1918432A (en) * | 2004-02-10 | 2007-02-21 | 株式会社荏原制作所 | Combustion device |
| US20100064691A1 (en) * | 2008-09-15 | 2010-03-18 | Laster Walter R | Flashback resistant pre-mixer assembly |
| US20100313569A1 (en) * | 2006-09-18 | 2010-12-16 | General Electric Company | Distributed-Jet Combustion Nozzle |
| CN202253758U (en) * | 2011-08-11 | 2012-05-30 | 中国航空动力机械研究所 | Air swirler |
| CN103017203A (en) * | 2012-12-06 | 2013-04-03 | 中国科学院工程热物理研究所 | Fractional combustion chamber |
| CN204084463U (en) * | 2014-09-01 | 2015-01-07 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of head of combustion chamber structure with cooling device |
| CN204665351U (en) * | 2015-03-31 | 2015-09-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The steady flame device of a kind of gas-turbine combustion chamber cold gas |
-
2015
- 2015-03-31 CN CN201510150221.1A patent/CN104764043B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1918432A (en) * | 2004-02-10 | 2007-02-21 | 株式会社荏原制作所 | Combustion device |
| US20100313569A1 (en) * | 2006-09-18 | 2010-12-16 | General Electric Company | Distributed-Jet Combustion Nozzle |
| US20100064691A1 (en) * | 2008-09-15 | 2010-03-18 | Laster Walter R | Flashback resistant pre-mixer assembly |
| CN202253758U (en) * | 2011-08-11 | 2012-05-30 | 中国航空动力机械研究所 | Air swirler |
| CN103017203A (en) * | 2012-12-06 | 2013-04-03 | 中国科学院工程热物理研究所 | Fractional combustion chamber |
| CN204084463U (en) * | 2014-09-01 | 2015-01-07 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of head of combustion chamber structure with cooling device |
| CN204665351U (en) * | 2015-03-31 | 2015-09-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The steady flame device of a kind of gas-turbine combustion chamber cold gas |
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| CN104764043B (en) | 2022-10-21 |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20191223 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Applicant after: CHINA UNITED HEAVY GAS TURBINE TECHNOLOGY Co.,Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Applicant before: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. |
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